Torch ignition device for nitrous oxide/hydrocarbon fuel rocket engine

A nitrous oxide and rocket engine technology, applied in rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problems of poor ignition reliability and difficulty in ignition, achieve reliable ignition, and meet the effect of multiple start-up requirements

Inactive Publication Date: 2013-12-18
SHANGHAI INST OF SPACE PROPULSION
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Most of the current nitrous oxide / hydrocarbon fuel engines are in the research stage of ground tests. The igniter mainly adopts electric spark direct ignition. This ignition method is only suitable for small thrust test pieces. Ignition is difficult and less reliable

Method used

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  • Torch ignition device for nitrous oxide/hydrocarbon fuel rocket engine

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Embodiment Construction

[0007] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0008] Such as figure 1 Shown is a nitrous oxide and propane rocket engine torch ignition device, which consists of a nitrous oxide electromagnetic valve seat (1), an igniter seat (2), a nitrous oxide catalytic decomposition chamber (3), and a propane electromagnetic valve seat (4), Outer Core (5), Inner Core (6), Flow Stabilizer (7), Propane Liquid Collection Chamber (8), Upstream Propane Injection Hole (9), Downstream Propane Injection Hole (10) , nitrous oxide collecting chamber (11), nitrous oxide injection hole (12), torch combustion chamber (13), nitrous oxide inlet (14), propane inlet (15) composition: pass through nitrous oxide The nitrous oxide in the nitrogen catalytic decomposition chamber (3) is catalytically decomposed, and the decomposition product is a high-temperature mixture of nitrogen and oxygen, and the mass flow rate of the nitrous oxide...

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Abstract

The invention discloses a technical field related to liquid rocket engines of aerospace propulsion systems, specifically a nitrous oxide and propane rocket engine torch ignition device, which is composed of nitrous oxide electromagnetic valve seats, igniter seats, and nitrous oxide catalytic decomposition Chamber, propane solenoid valve seat, outer core body, inner core body, flow stabilizer, propane liquid collection chamber, upstream propane injection hole, downstream propane injection hole, nitrous oxide liquid collection chamber, nitrous oxide injection Orifice, torch combustion chamber, nitrous oxide inlet, and propane inlet. The decomposition product of the catalytic decomposition chamber forms a primary torch with upstream propane, and the nitrous oxide from the radial injection hole forms a secondary torch with downstream propane, which is used for The rocket motor ignites and starts. The invention can obtain a stable and high-energy ignition torch, and can realize reliable ignition and start of a rocket engine combined with nitrous oxide and propane propellant.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engines, in particular to a torch ignition device that can be applied to nitrous oxide / hydrocarbon fuel rocket engines in aerospace propulsion systems. Background technique [0002] The nitrous oxide / hydrocarbon fuel propellant combination has acceptable specific impulse performance (vacuum specific impulse 280s-330s), is safe, non-toxic, and storable, and is one of the important development directions of non-toxic aerospace propulsion technology. The high safety and ease of operation make the nitrous oxide / hydrocarbon fuel rocket engine have wide application prospects in the fields of launch vehicles, missile weapons and space transportation. [0003] The current nitrous oxide / hydrocarbon fuel engines are mostly in the research stage of ground tests. The igniter mainly adopts direct spark ignition. This ignition method is only suitable for small thrust test pieces. Ignition is difficult an...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/95F02K9/42
Inventor 周海清刘俊林国庆
Owner SHANGHAI INST OF SPACE PROPULSION
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